The 'PolarBrowser' application, a polar file converter is available
in the software section at:
http://www.MH-AeroTools.de/airfoils/
MH 110
smooth surface (r=0)
Copyright 2000-2004 Martin Hepperle
polar
500000.0
0.00000
Alpha
Cl
Cd
Cm
TU
TL
SU
SL
-4.000
-0.440
0.01130
0.0443
-99.999
-99.999
-99.999
-99.999
-3.000
-0.330
0.00780
0.0434
-99.999
-99.999
-99.999
-99.999
-2.000
-0.220
0.00740
0.0425
-99.999
-99.999
-99.999
-99.999
-1.000
-0.110
0.00740
0.0416
-99.999
-99.999
-99.999
-99.999
0.000
0.000
0.00750
0.0404
-99.999
-99.999
-99.999
-99.999
1.000
0.110
0.00790
0.0392
-99.999
-99.999
-99.999
-99.999
2.000
0.220
0.00820
0.0379
-99.999
-99.999
-99.999
-99.999
4.000
0.440
0.00900
0.0358
-99.999
-99.999
-99.999
-99.999
5.500
0.610
0.00970
0.0344
-99.999
-99.999
-99.999
-99.999
6.000
0.660
0.01010
0.0339
-99.999
-99.999
-99.999
-99.999
6.500
0.710
0.01040
0.0338
-99.999
-99.999
-99.999
-99.999
7.000
0.740
0.01390
0.0406
-99.999
-99.999
-99.999
-99.999
8.000
0.730
0.01540
0.0550
-99.999
-99.999
-99.999
-99.999
9.000
0.740
0.01730
0.0598
-99.999
-99.999
-99.999
-99.999
polar
700000.0
0.00000
Alpha
Cl
Cd
Cm
TU
TL
SU
SL
-4.000
-0.440
0.01060
0.0443
-99.999
-99.999
-99.999
-99.999
-3.000
-0.330
0.00770
0.0434
-99.999
-99.999
-99.999
-99.999
-2.000
-0.220
0.00700
0.0425
-99.999
-99.999
-99.999
-99.999
-1.000
-0.110
0.00690
0.0416
-99.999
-99.999
-99.999
-99.999
0.000
0.000
0.00690
0.0406
-99.999
-99.999
-99.999
-99.999
1.000
0.110
0.00720
0.0396
-99.999
-99.999
-99.999
-99.999
2.000
0.220
0.00750
0.0383
-99.999
-99.999
-99.999
-99.999
4.000
0.440
0.00820
0.0359
-99.999
-99.999
-99.999
-99.999
5.500
0.610
0.00890
0.0344
-99.999
-99.999
-99.999
-99.999
6.000
0.660
0.00910
0.0339
-99.999
-99.999
-99.999
-99.999
6.500
0.720
0.00940
0.0334
-99.999
-99.999
-99.999
-99.999
7.000
0.750
0.01300
0.0378
-99.999
-99.999
-99.999
-99.999
8.000
0.760
0.01440
0.0522
-99.999
-99.999
-99.999
-99.999
9.000
0.770
0.01620
0.0594
-99.999
-99.999
-99.999
-99.999
polar
1000000.0
0.00000
Alpha
Cl
Cd
Cm
TU
TL
SU
SL
-4.000
-0.440
0.01010
0.0443
-99.999
-99.999
-99.999
-99.999
-3.000
-0.330
0.00740
0.0434
-99.999
-99.999
-99.999
-99.999
-2.000
-0.220
0.00670
0.0425
-99.999
-99.999
-99.999
-99.999
-1.000
-0.110
0.00650
0.0416
-99.999
-99.999
-99.999
-99.999
0.000
0.000
0.00650
0.0406
-99.999
-99.999
-99.999
-99.999
1.000
0.110
0.00660
0.0396
-99.999
-99.999
-99.999
-99.999
2.000
0.220
0.00680
0.0386
-99.999
-99.999
-99.999
-99.999
4.000
0.440
0.00750
0.0361
-99.999
-99.999
-99.999
-99.999
5.500
0.610
0.00810
0.0345
-99.999
-99.999
-99.999
-99.999
6.000
0.660
0.00840
0.0340
-99.999
-99.999
-99.999
-99.999
6.500
0.720
0.00860
0.0334
-99.999
-99.999
-99.999
-99.999
7.000
0.760
0.01200
0.0363
-99.999
-99.999
-99.999
-99.999
8.000
0.800
0.01350
0.0480
-99.999
-99.999
-99.999
-99.999
9.000
0.800
0.01510
0.0584
-99.999
-99.999
-99.999
-99.999
rough surface (r=3)
Copyright 2000-2004 Martin Hepperle
polar
500000.0
0.00000
Alpha
Cl
Cd
Cm
TU
TL
SU
SL
-4.000
-0.440
0.01200
0.0443
-99.999
-99.999
-99.999
-99.999
-3.000
-0.330
0.01090
0.0434
-99.999
-99.999
-99.999
-99.999
-2.000
-0.220
0.01030
0.0425
-99.999
-99.999
-99.999
-99.999
-1.000
-0.110
0.00980
0.0416
-99.999
-99.999
-99.999
-99.999
0.000
0.000
0.00960
0.0406
-99.999
-99.999
-99.999
-99.999
1.000
0.110
0.00930
0.0396
-99.999
-99.999
-99.999
-99.999
2.000
0.220
0.00930
0.0386
-99.999
-99.999
-99.999
-99.999
4.000
0.440
0.00950
0.0364
-99.999
-99.999
-99.999
-99.999
5.500
0.610
0.01000
0.0347
-99.999
-99.999
-99.999
-99.999
6.000
0.660
0.01050
0.0343
-99.999
-99.999
-99.999
-99.999
6.500
0.710
0.01090
0.0342
-99.999
-99.999
-99.999
-99.999
7.000
0.740
0.01390
0.0407
-99.999
-99.999
-99.999
-99.999
8.000
0.730
0.01550
0.0555
-99.999
-99.999
-99.999
-99.999
9.000
0.740
0.01730
0.0604
-99.999
-99.999
-99.999
-99.999
polar
700000.0
0.00000
Alpha
Cl
Cd
Cm
TU
TL
SU
SL
-4.000
-0.440
0.01140
0.0443
-99.999
-99.999
-99.999
-99.999
-3.000
-0.330
0.01050
0.0434
-99.999
-99.999
-99.999
-99.999
-2.000
-0.220
0.01000
0.0425
-99.999
-99.999
-99.999
-99.999
-1.000
-0.110
0.00960
0.0416
-99.999
-99.999
-99.999
-99.999
0.000
0.000
0.00930
0.0406
-99.999
-99.999
-99.999
-99.999
1.000
0.110
0.00920
0.0396
-99.999
-99.999
-99.999
-99.999
2.000
0.220
0.00900
0.0386
-99.999
-99.999
-99.999
-99.999
4.000
0.440
0.00910
0.0364
-99.999
-99.999
-99.999
-99.999
5.500
0.610
0.00950
0.0347
-99.999
-99.999
-99.999
-99.999
6.000
0.660
0.00980
0.0341
-99.999
-99.999
-99.999
-99.999
6.500
0.710
0.01010
0.0337
-99.999
-99.999
-99.999
-99.999
7.000
0.750
0.01310
0.0379
-99.999
-99.999
-99.999
-99.999
8.000
0.760
0.01450
0.0526
-99.999
-99.999
-99.999
-99.999
9.000
0.770
0.01620
0.0601
-99.999
-99.999
-99.999
-99.999
polar
1000000.0
0.00000
Alpha
Cl
Cd
Cm
TU
TL
SU
SL
-4.000
-0.440
0.01090
0.0443
-99.999
-99.999
-99.999
-99.999
-3.000
-0.330
0.01010
0.0434
-99.999
-99.999
-99.999
-99.999
-2.000
-0.220
0.00970
0.0425
-99.999
-99.999
-99.999
-99.999
-1.000
-0.110
0.00940
0.0416
-99.999
-99.999
-99.999
-99.999
0.000
0.000
0.00910
0.0406
-99.999
-99.999
-99.999
-99.999
1.000
0.110
0.00900
0.0396
-99.999
-99.999
-99.999
-99.999
2.000
0.220
0.00890
0.0386
-99.999
-99.999
-99.999
-99.999
4.000
0.440
0.00890
0.0364
-99.999
-99.999
-99.999
-99.999
5.500
0.610
0.00920
0.0347
-99.999
-99.999
-99.999
-99.999
6.000
0.660
0.00930
0.0341
-99.999
-99.999
-99.999
-99.999
6.500
0.720
0.00970
0.0335
-99.999
-99.999
-99.999
-99.999
7.000
0.760
0.01230
0.0364
-99.999
-99.999
-99.999
-99.999
8.000
0.800
0.01360
0.0482
-99.999
-99.999
-99.999
-99.999
9.000
0.800
0.01520
0.0588
-99.999
-99.999
-99.999
-99.999